Segmented self-destruction precipitation enhancement hail suppression rocket controlled by time schedule controller

Abstract

The invention discloses a segmented self-destruction rain enhancement and hail suppression rocket controlled by a time schedule controller, and relates to the technical field of artificial rain enhancement and hail suppression rockets. The device comprises a catalysis bin assembly, an engine assembly and an empennage assembly, and the catalysis bin assembly, the engine assembly and the empennage assembly are connected through reducing sleeve assemblies. An explosion self-destruction device is adopted as a safe landing device, a segmented self-destruction device is arranged in a rocket body engine and a tail segment assembly in advance, a time schedule controller outputs an ignition signal according to binding information, an empennage assembly, an engine assembly and a catalytic bin assembly are exploded into floccules not larger than 100 g and fall onto the ground, self-destruction of all the assemblies is reliable, and the safety of landing is guaranteed. The rocket body wreckage preventing device can effectively reduce damage of rocket body wreckage to personnel, buildings, farmlands, livestock and the like, any one of the ignition loops of the time schedule controller does not affect performance of other loops during working, fire spurting is avoided, space is saved, and the function is reliable.

Description

Technical Field

[0001] The invention relates to the technical field of artificial rainfall enhancement and hail prevention rockets, in particular to a segmented self-destruction rainfall enhancement and hail prevention rocket controlled by a timing controller. Background Art

[0002] Weather modification is based on the research results of cloud and fog precipitation physics, especially artificial rainfall experiments with cumulus clouds as the object;

[0003] At present, the hail prevention and rain enhancement tools at home and abroad have gone through different development stages, from homemade guns and homemade rockets to anti-aircraft guns and new rockets.

[0004] The anti-hail and rain-enhancing operations of homemade artillery and anti-aircraft artillery are mainly carried out through the one-time work of the pyrotechnic device in the shell, which converts chemical heat energy into kinetic energy, overcomes the gravity and launches the weather-affecting substances into the atmosphere. Since the shells are fired at a low altitude, the expected effect is often not achieved. Homemade rockets and new rockets all adopt the rocket launch mechanism. Through the delayed action of the delayed ignition device, the rocket is launched to a predetermined high point. After the delayed ignition device completes the parachute opening function, it continues to work for a certain period of time, which can better spread the weather-affecting substances in the predetermined atmosphere and achieve good anti-hail and rain-enhancing effects. However, this method currently generally has problems such as high misfire rate and misfire rate of the delayed fuze, short delay, and poor delay accuracy.

[0005] Existing technical solutions:

[0006] The existing rain-increasing and hail-preventing rockets are mainly composed of a rocket body, a delay tube, a parachute compartment, a parachute opening device, a fixed-explosion delay tube detonator, and a functional part;

[0007] The delay tube is arranged at the front end of the engine, the parachute and the parachute opening device are fixed on the delay tube and installed in the parachute cabin, and the fixed explosion delay tube and the detonator are inserted into the detonator seat at the front end of the parachute cabin, and the fixed explosion delay tube is inserted into the round hole at the front end of the delay tube through the parachute opening device, and the functional part is connected to the parachute cabin, and it is delayed for a predetermined time through the delay tube to transmit fire to the fixed explosion delay tube, and at the same time, the parachute opening device is stimulated and the parachute cabin is pushed forward together with the functional part, the parachute is opened, and the detonator is detonated after the predetermined time of the fixed explosion delay tube, thereby directly detonating the functional part, so as to achieve the purpose of spreading the catalyst;

[0008] However, the above prior art still has some defects:

[0009] 1. The delay time is inaccurate and the operation is unreliable. Because the delay devices in rockets are all pyrotechnic delay tubes, the delay time is difficult to be accurate and the operation is unreliable due to the influence of raw materials, equipment, processing technology, assembly process and production environment during the production process;

[0010] 2. After the rocket is launched, the fixed explosion delay tube works in a high altitude and high negative pressure environment, which is prone to misfire and flameout, thus causing the parachute opening device and functional parts to fail;

[0011] 3. The problem of rocket frame explosion. Because most of the parts in the rocket production process are industrial pyrotechnic parts, it is inevitable that some pyrotechnic parts will have quality problems, causing the rocket to be stranded in the arrow track after launch. When the predetermined delay time is reached, the rocket's energy department will work and blow up the arrow track;

[0012] In view of the above problems, the inventor proposes a segmented self-destructive rain-increasing and hail-preventing rocket controlled by a timing controller to solve the above problems. Summary of the invention

[0013] In order to solve the above problems, the purpose of the present invention is to provide a segmented self-destruction rain-increasing and hail-preventing rocket controlled by a timing controller.

[0014] In order to solve the above technical problems, the present invention adopts the following technical solutions: a segmented self-destruction rain-increasing and hail-preventing rocket controlled by a timing controller, comprising a rocket body, on which a catalytic chamber assembly, an engine assembly and a tail assembly are arranged, and the catalytic chamber assembly, the engine assembly and the tail assembly are connected by an adapter sleeve assembly;

[0015] The catalytic chamber assembly is provided with a catalyst and a catalyst ignition device, the engine assembly is provided with a timing controller, a segmented self-destruction device and an engine ignition device, and the tail wing assembly includes a nozzle, a drug baffle and a tail wing.

[0016] Preferably, the adapter sleeve assembly includes an adapter sleeve, a sealing plug and a conductive half ring, the adapter sleeve is a rotating part with a partition plate inside, the partition plate is provided with a conductive screw, the catalyst ignition device is arranged in a chamber of the adapter sleeve close to the catalyst side, and is connected to the catalyst ignition end of the timing controller through a wire and a conductive screw to form a catalyst ignition circuit;

[0017] A groove for fixing two non-contacting conductive half rings is provided on the outer periphery of the side wall of the adapter sleeve away from the catalyst;

[0018] The timing controller is arranged in a chamber on a side of the adapter sleeve away from the catalyst, and a power supply end of the timing controller is connected to a conductive half ring through a conductive screw and a wire.

[0019] Preferably, the engine assembly further comprises an intermediate bottom assembly, wherein the intermediate bottom assembly comprises an intermediate bottom and a conductive copper foil;

[0020] The middle bottom is a rotating part with a partition inside. Two non-contacting conductive copper foils are arranged on the outer periphery of the front end side wall of the middle bottom. The front end side wall of the middle bottom is connected to the side wall of the rear end of the adapter sleeve through a conductive screw. A hole for the wire to pass through is arranged on the partition of the middle bottom.

[0021] Preferably, the segmented self-destruct device comprises a segmented self-destruct device igniter, a self-destruct charge and a delay charge assembly, the self-destruct charge is pressed into the cavity of the segmented self-destruct device, the segmented self-destruct device igniter is arranged in the middle bottom, and the fuse of the segmented self-destruct device igniter is connected to the timing controller and the ignition end of the segmented self-destruct device igniter through the internal via hole of the middle bottom to form an ignition circuit of the segmented self-destruct device;

[0022] The engine ignition device is arranged in the rear end chamber of the segmented self-destruction device, and the engine ignition device is connected to the engine ignition end of the timing controller by a wire through the middle hole of the segmented self-destruction device.

[0023] Preferably, the engine assembly further comprises a combustion chamber assembly.

[0024] Preferably, a prefabricated stress groove is engraved inside the tail wing, and the tail wing is fixed using circumferential positioning screws.

[0025] Preferably, the delay charge assembly, engine ignition device and segmented self-destruction device ignition device are all designed with double insurance redundancy.

[0026] Preferably, the conductive half ring is in contact with a conductive contact on the launcher rail.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] 1. In the present invention, an explosive self-destruct device is used as a safe landing device. The segmented self-destruct device is pre-placed inside the rocket body engine and tail section assembly. The timing controller outputs an ignition signal according to the binding information, and the tail wing assembly, the engine assembly, and the catalyst chamber assembly are exploded into floccules not larger than 100g that fall to the ground. Each assembly self-destructs reliably, which can effectively reduce the damage of the rocket body debris to personnel, buildings, farmland, livestock, etc.;

[0029] 2. In the present invention, through the ignition circuit of the timing controller, any ignition circuit will not affect the performance of other circuits when working, thus avoiding fire, saving space and having reliable function;

[0030] 3. In the present invention, the timing controller adopts an electronic delay module that can be bound on site. Before launching, the timing controller engine ignition, catalyst ignition, and segmented self-destruction device ignition output time are bound with time information and altitude information at the same time, avoiding the use of a large number of pyrotechnic delay tubes as delay devices. The timing output is accurate and reliable. At the same time, on-site binding can meet the operation requirements of different regions and seasons;

[0031] 4. In the present invention, the engine ignition device, catalyst ignition device, segmented self-destruction device ignition device, and delay charge assembly all adopt a double insurance redundancy design, with a low failure rate and high operational reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0033] Figure 1 It is a schematic diagram of the structure of the present invention.

[0034] In the figure: 10, rocket body; 1, catalyst chamber assembly; 2, engine assembly; 3, tail assembly; 11, catalyst; 12, catalyst ignition device; 21, timing controller; 22, segmented self-destruct device; 23, engine ignition device; 31, nozzle; 32, powder baffle; 33, tail. DETAILED DESCRIPTION

[0035] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0036] Example: Figure 1 As shown, the present invention provides a segmented self-destruction rain-increasing and hail-preventing rocket controlled by a timing controller, comprising a rocket body 10, on which a catalytic chamber assembly 1, an engine assembly 2 and a tail assembly 3 are arranged, and the catalytic chamber assembly 1, the engine assembly 2 and the tail assembly 3 are connected by an adapter sleeve assembly;

[0037] The catalytic chamber assembly 1 is provided with a catalyst 11 and a catalyst igniter 12 , the engine assembly 2 is provided with a timing controller 21 , a segmented self-destruction device 22 and an engine igniter 23 , and the tail assembly 3 includes a nozzle 31 , a drug baffle 32 and a tail wing 33 .

[0038] The adapter sleeve assembly includes an adapter sleeve, a sealing plug and a conductive half ring. The adapter sleeve is a rotating part with a partition plate inside. The partition plate is provided with a conductive screw. The catalyst ignition device 12 is arranged in a chamber of the adapter sleeve close to the catalyst 11 side, and is connected to the catalyst ignition end of the timing controller 21 through a wire and a conductive screw to form an ignition circuit of the catalyst 11.

[0039] A groove for fixing two non-contacting conductive half rings is provided on the outer periphery of the side wall of the adapter sleeve away from the catalyst 11;

[0040] The timing controller 21 is disposed in a chamber on a side of the adapter sleeve away from the catalyst 11 , and a power supply end of the timing controller 21 is connected to a conductive half ring through a conductive screw and a wire.

[0041] The engine assembly 2 further includes an intermediate bottom assembly, which includes an intermediate bottom and a conductive copper foil;

[0042] The middle bottom is a rotating part with a partition inside. Two non-contacting conductive copper foils are arranged on the outer periphery of the front side wall of the middle bottom. The front side wall of the middle bottom is connected to the side wall of the rear end of the adapter sleeve through a conductive screw. A hole is arranged on the partition of the middle bottom for the wire to pass through.

[0043] The segmented self-destruction device 22 includes a segmented self-destruction device igniter, a self-destruction charge and a delay charge assembly. The self-destruction charge is pressed into the cavity of the segmented self-destruction device 22. The segmented self-destruction device igniter is arranged in the middle bottom. The fuse of the segmented self-destruction device igniter is connected to the timing controller 21 through the internal via hole of the middle bottom. The ignition end of the segmented self-destruction device igniter constitutes an ignition circuit of the segmented self-destruction device 22.

[0044] The engine ignition device 23 is arranged in the rear end chamber of the segmented self-destruction device 22 , and the engine ignition device 23 is connected to the engine ignition end of the timing controller 21 by a wire through the middle hole of the segmented self-destruction device 22 .

[0045] The engine assembly 2 also includes a combustion chamber assembly.

[0046] A prefabricated stress groove is engraved inside the tail wing 33, and the tail wing 33 is fixed using circumferential positioning screws.

[0047] The delay charge assembly, the engine igniter 23 and the segmented self-destruction device igniter are all designed with double insurance redundancy.

[0048] The conductive half ring contacts the conductive contact on the launcher rail.

[0049] Working principle: When in use, first, the segmented self-destructing rain-enhancing and hail-preventing rocket is loaded into the launcher rail, and the locking and blocking mechanism of the launcher rail is accurately positioned, the conductive half ring on the segmented self-destructing rain-enhancing and hail-preventing rocket contacts the conductive contact on the launcher rail, and the power supply end of the timing controller 21 receives power and enters the working state;

[0050] According to the local temperature, air pressure, altitude, cloud height and other information of the launch site, the timing controller 21 is bound with the time and altitude information to respectively set the engine ignition time, the catalyst 11 ignition time and the segmented self-destruction device 22 ignition time. The timing controller 21 outputs the engine ignition signal, and the engine ignition device 23 ignites the propellant after receiving the signal, thereby providing flight power for the segmented self-destruction rain-increasing and hail-prevention rocket.

[0051] After the catalyst ignition circuit of the timing controller 21 delays for a predetermined time or the segmented self-destruction rain-increasing and hail-prevention rocket reaches a predetermined cloud height, the catalyst ignition end of the timing controller 21 outputs an ignition signal, and the catalyst ignition device 12 ignites and ignites the catalyst 11. After the catalyst ignition end of the timing controller 21 outputs a signal, a predetermined time is delayed, and the timing controller 21 and the ignition end of the segmented self-destruction device 22 output a signal to the segmented self-destruction device ignition device, and the segmented self-destruction device 22 is ignited, and the gunpowder gas continues to expand until the combustion chamber assembly is exploded into fragments;

[0052] At this time, the entire segmented self-destructive rain-making and hail-prevention rocket was broken into flocs no larger than 100g and fell to the ground. The delay was calculated based on information such as the local temperature, air pressure, altitude, and cloud height of the launch site.

[0053] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. A segmented self-destructing rain-increasing and hail-preventing rocket controlled by a timing controller, comprising a rocket body (10), characterized in that: The arrow body (10) is provided with a catalytic chamber assembly (1), an engine assembly (2) and a tail assembly (3), and the catalytic chamber assembly (1), the engine assembly (2) and the tail assembly (3) are connected via an adapter sleeve assembly; The catalytic chamber assembly (1) is provided with a catalyst (11) and a catalyst igniter (12); the engine assembly (2) is provided with a timing controller (21), a segmented self-destruction device (22) and an engine igniter (23); and the tail assembly (3) comprises a nozzle (31), a drug baffle (32) and a tail (33).

2. A segmented self-destruction rain-increasing and hail-preventing rocket controlled by a timing controller as claimed in claim 1, characterized in that: The adapter sleeve assembly comprises an adapter sleeve, a sealing plug and a conductive half ring, the adapter sleeve is a rotating part with a partition plate inside, the partition plate is provided with a conductive screw, the catalyst ignition device (12) is arranged in a chamber of the adapter sleeve close to the catalyst (11) side, and is connected to the catalyst ignition end of the timing controller (21) through a wire and a conductive screw to form a catalyst (11) ignition circuit; A groove for fixing two non-contacting conductive half rings is formed on the outer periphery of the side wall of the adapter sleeve away from the catalyst (11); The timing controller (21) is arranged in a chamber on a side of the adapter sleeve away from the catalyst (11), and a power supply end of the timing controller (21) is connected to a conductive half ring via a conductive screw and a wire.

3. A segmented self-destruction rain-increasing and hail-preventing rocket controlled by a timing controller as claimed in claim 1, characterized in that: The engine assembly (2) further comprises an intermediate bottom assembly, wherein the intermediate bottom assembly comprises an intermediate bottom and a conductive copper foil; The middle bottom is a rotating part with a partition inside. Two non-contacting conductive copper foils are arranged on the outer periphery of the front end side wall of the middle bottom. The front end side wall of the middle bottom is connected to the side wall of the rear end of the adapter sleeve through a conductive screw. A hole for the wire to pass through is arranged on the partition of the middle bottom.

4. A segmented self-destruction rain-increasing and hail-preventing rocket controlled by a timing controller as claimed in claim 3, characterized in that: The segmented self-destruction device (22) comprises a segmented self-destruction device igniter, a self-destruction charge and a delay charge assembly, wherein the self-destruction charge is pressed into a cavity of the segmented self-destruction device (22), the segmented self-destruction device igniter is arranged in the middle bottom, and the fuse of the segmented self-destruction device igniter is connected to the timing controller (21) through the internal via hole of the middle bottom, and the ignition end of the segmented self-destruction device igniter forms an ignition circuit of the segmented self-destruction device (22); The engine ignition device (23) is arranged in the rear end chamber of the segmented self-destruction device (22), and the engine ignition device (23) is connected to the engine ignition end of the timing controller (21) by a wire through a middle hole of the segmented self-destruction device (22).

5. A segmented self-destruction rain-increasing and hail-preventing rocket controlled by a timing controller as claimed in claim 1, characterized in that: The engine assembly (2) also includes a combustion chamber assembly.

6. A segmented self-destruction rain-increasing and hail-preventing rocket controlled by a timing controller as claimed in claim 1, characterized in that: A prefabricated stress groove is engraved inside the tail wing (33), and the tail wing (33) is fixed using circumferential positioning screws.

7. A segmented self-destruction rain-increasing and hail-preventing rocket controlled by a timing controller as claimed in claim 4, characterized in that: The delay charge assembly, the engine ignition device (23) and the segmented self-destruction device ignition device are all designed with double insurance redundancy.

8. A segmented self-destruction rain-increasing and hail-preventing rocket controlled by a timing controller as claimed in claim 2, characterized in that: The conductive half ring is in contact with the conductive contact point on the launcher rail.

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